Bomb sighting device



EI35-1+01 SR m 25,115,041 EBCH RGOM,

. jv u @ROSS Hmm-NGE May 24, 1938. 1 ESTOPPEY 2,118,041

y BOMB SIGHTING DEVICE Y Original Filed Sept. 5, 1959 6 Sheets-Sheet l V yf we si Qs. W 0 TTORNE Y May 24 1938- G, L. ESTOPPEY BOMB SIGHTING nEvlcE 6 Sheets-Sheet 3 Original FiIed Sept. 5, 193D mfY May 24, 1938. G. 1 ESTOPPEY 2,118,041- Uf BOMB SIGHTING DEVICE v v wir J original Filed sept. 5, 1930 e sheets-snep:l U.

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up: TYP: 1w: TYPE /23` A A B l; Eg! ma AUTO NAND /22 m l?! AUTO TYPETYPTYPET M c c n n INVENTOR May 24, 1938. G. L.. EsToPPEY v 2118,041.

BOMB SIGHTING' DVICE Y Original Filed Sept. 5, 193!) 6 Sheets-Sheet 5 'l A F/. /8- N 52 L1:g/.s' f 14a 90' fr Y 6 l l alf f f s V" f'k, 0.-.. /59 y IN VENTO/ A TTORNEY yMay 24,119.38. L, ESTOPPEY 2,118,041

Bona SIGHTING .a-NICE original Filed sept. s, 193s e sheets-sheet s 'lvg, Z n F76. E/ Y l Patented May 2,4, 1938 v v UNITED STATES PATENTv OFFICE Application September 5, 1930, Serial No. 4719.950 f Renewed May 21, 1936 24 Claims. (Cl. 33t-46.5)

This invention relates to sighting devices such as are -used in the dropping of bombs or projectiles from aircraft, or to similar devices where there is relative movement between an objective and the sighing device and the two are at different elevations.

One object of the invention is the provision 'of a sighting device of this character provided with a movable sighting member, and having an adjustable timing member, means being pro- 2 A further object of the invention is the provision of a sighting member for the release of bombs from aircraft, having a sighting member and an adjustable timing member the latter being adjustable along an ordinate of a coordinate system in accordance with the altitude and automatically positioned along the other ordinate in accordance with the speed of the movable sight-` ing member. Another object of the invention is the provision of a sighting device having a movable sighting member and an adjustable timing member supported in a. novel manner to provide a very accurate and easily operated sight, which can be manipulated in a very short space of time.

Another object of the invention is the provision of means for adjusting the sight to make trail corrections, longitudinally of the sight, for compensating for air resistance of the bomb in 40 accordance with its terminal velocity. time lag; air speed, altitude of the sight, drift angle, angle of approach with respect to a movable objective, altitude of the objective, and temperature afiecting the terminal velocity of the bomb. Another object of the invention is the provision of means for adjusting the sight to makelateral corrections compensating for the resistance of the wind against the bomb, when flying cross wind, this compensation being corrected in accordance with the air resistance of the bomb according to its terminal velocity, time lag, air speed, altitude of the sight, drift angle, angle of approach with respect to a movable objective, altitude of the objective, and temperature affecting the terminal velocity of the bomb.

Another object of the invention is the provision of a time saving scale provided for rapid adjustment of the position of the sighting member before the synchronization of the sighting device with the objective so as to reduce the time oi 5 bombing operation.

Another object of the invention is the provision. of means operable during the synchronizing operation for automatically moving the sighting member as the speed of the sighting member is 10 increased or decreased to return the objective to the line of sight. y

Another object oi the invention ls the provision of meesfor.mng'a.writtesign--inthe'iield o! l visionjfor, warning theY operatorthat the bomb is 15 about to be dropped or that the bomb dropping weight of the moving parts of the instrument so that the instrument can remain in avertical position.

Still other objects and advantages of the in- 30 vention will be apparent from the following description, the appended claims, and the accompanying drawings in which- Fig. 1 is a top plan view of the sighting device embodying the present invention; 35

' Fig. 2 is a rear elevation of the sighting device;

Fig. 3 is a side elevation of the sighting device;

Fig. 4 isa vertical sectional view taken on the 4o line 4--4 of Fig. 1 through the plvoally mounted supporting housing and on the line 5 through the top of the standard;

Fig. 5 is a horizontal section on the line 5-5 oi Fig. 4, also' showing part ci the pilot direct- 45 lng device;

Fig. 6 is a horizontal section on line 5--5 of Fig. 2;

Fig. 7 is a horizontal section on line l-l oi Fig. 4;

Fig. 8 is a transverse vertical section of the sighting device on the line 8 8 oi Fig. 1;

Fig. 9 is a transverse vertical section on line 9-9 of Fig. 6, showing part of the pilot director mechanism; I

Eg. is a sectional view of the pilot director indicator;

Fig. 11 is a central vertical sectional view of the main support of the sighting device: 5 Fig. 12'is a front viewof the air density dial; Figs. l13, 14, and 15 are sectional views o1' the sighting member, showing the arrangement of the signal lamps device;

Fis'. 15 shows a developed view of the altitude l0 scale and personal lag scale;

Fig. 17 showsa developed view of a cylinder shield used in connection with the altitude dial and personal lag scale and type of bomb;

Fig. 18 is a diagrammatic representation of the 15 correcting device relative to type of bomb, air

speed, wind speed, drift angle, altitude and air ylng in thedirection of the wind or making density;

Fig. 19 is a diagrammatic representation 'of the space factors and angles ofthe sighting device; 20 Fig. 20 is a sectional view of the automatic stop used in relation with the index of the shield here above mentioned.

Fig. 21 is a diagrammatic representation of the space factors and angles in a three coordinate system, for a moving objective:

Fig. 22 is a diagrammatic plan view corresponding to Fig. 21; and

Fig. 23 is a detail showing the correcting device for dropping the bomb short of the objective. 111e sighting device of this invention is herein shown as a bomb sight adapted for the releasing of bombs or projectiles from aircraft, butwitis top e understood that the invention is susceptible "to other useswvhere there" isV relative`movement between anbbjectivehnd Athe sight and Vthe vtwo are at diil'erent elevations. The sight, as shown, embodies a standard 2| (Fig. 1l) which may be mounted in e. suitable position on an aircraft or the like so that the xed post 22 within this standard is vertically positioned on the aircraft, the standard 2| being movable about the post 22. The standard 2| forms a mount for the supa porting means 23 which forms a supporting housing for various operating parts of the bomb 45 sight. As shown in Fig. 4 the supporting means or housing 23 is supported by thegimbal mountv ing 24 (Fig. 4) near its top from an upper part of the standardv 2| so that housing 23 hangs like a pendulum and forms a standard of position with relation to the aircraft.

A movable sighting member is provided which may be caused to follow the movements of the objective, and while this movable sighting member may be of any desired character, it is herein shown and described for purposes of illustration as an optical device 25 carried by a link 25 and having a top sight bead 21 and a bottom sight bead 28 which may be aligned with the eye and' with the objective so that when the sights 2l and 28 thus aligned with the eye appear to follow the movement of the objective, the sighting member is ready for synchronizing operation. As shown the carrying or sighting link 25 is provided inside the housing 23. The lower end of the sighting link 25 is slotted at 29 and engages a pin 30 on micrometric'screw 32, the latter being mounted in suitable bearings 33 in the housing 23 and extending horizontally across the housing. Thus when the screw 32 is rotated at the proper speed the pin 3i) operating in the slotS causes the sighting link 25 to pivot about its upper end so that the optical line follows the objective in synchronism with its apparent movement.

7'5 The bearing sleeve 34 fixed to the upper end a nut 3| which is in threaded engagement with a of the sighting link 25 pivots about stud 35 which is fixed to a triangular swinging frame 36 which isy pivotally supported at its lower ends. VThe' upper end of frame 35 pivotally carries a slide 33 on axis 3l, the slidebeing movable transversely in the guide 39 which forms a part of another slide 40 movable longitudinally in a guide 4| xed to the main housing 23, as apparent from Figs. 4, 6, and 8. The lower part of the frame 35 has two bearing supports 42 and 43 which turn and slide longitudinally on the end parts of the micrometric" screw 32.

A slot in the lower end of the frame slidably receives an arm projection 44 of the nut 3| to restrain the nut from turning. 'Ihe slide 40' is a' part of the correcting device for making trail Acorrections if ground coursel components of the trail corrections if ying adrift. By means of the slide 40, the-upper end of the sighting member may be' moved longitudinally of the bomb sight by several control devices that will be later described.

and the slide 38 is a part of the wind deflection correcting device so that the upper end of the movable sighting member may bew moved laterally in accordance with the wind deflection so that the optical line of the sighting member 25 moves along an inclined piane which is properly inclined to the'vertical. (See Fig. 8.)

Within the housing 23 is a suitable power device such as an electric motor 4S (Fig. 4) of the constant speed type, this motor preferably .having an automatic governor 4l which makes and breaks an electrical connection 48 so that the speed of the motor is maintained substantially constant. This motor is connected by suitable leads to a battery 43 or other source of electrioity suitably` located on thev aircraft. The motor shaft Sil drives a worm 5| which meshes with worm wheel 52, the worm and worm wheel being suitably supported in bearings in a bracket 53 which is fastened on the supporting housing 23. Theworm wheel 52 is carried on a shaft to which is fastened a friction disc 54. Engaging this friction disc, which forms the driving member of a variable speed transmission mechanism between the motor 4B and the screw 32, is a driven friction wheel 55 suitably mounted in a bracket guide 56.' This bracket guide is in slid ing engagement with a transverse shaft 51 which is fixed by suitable key and slot connections to the friction wheel 55, the slot 53 in this shaft extending suillciently far so that the friction wheel 55 may be moved from the center of the disc 54 to its peripheral portionwhile in rotational driving connection with the shaft 51. The guide bracket 58 is parallel to the transverse shaft 5l, both of these shafts being suitably mounted at their ends in bearings provided in the supporting housing. The guide bracket 56 being threaded on shaft 59, as the latter is rotated the position of the guide bracket is adjusted, and this in turn adjusts the speed of rotation of the shaft 5l since the position of the friction wheel .S5-is moved towards or away from the center of driving disc 54. The shaft 5l drives the micrometric screw 32 through gear 60 and differential 6|. The purpose of the diierential 5| is to permit movement of the screw 32 to set the sighting link 25 at the minimum pick-up angle corresponding to altitude and air speed without corresponding movement of the shaft 5l when the motor ls at rest. Preferably the differential 6| embodies planetary gears 5|' carried on arms which are xed to the gear lll, the planetary 'gears 6I 2,118,041 meshing with a. sun gear on the end of shaft 32 and with a large outside gear which meshes with a gear Si) on shaft 5T. VIt will thus be apparent that the gear S8 may be rotated manually to rotate the screw 32 without imparting movement to the large outside gear of the differential meshing with gear Sil, but on the other hand when the gear 6G is rotated it will impart rotational movements to the screw 32 at a proportionate speed.

A combined altitude and airspeed scale $2 is engraved on a tube B3, see Figs. 3 and 8. The tube 63 is controlled rotatably by-means of a knob 64 at the end of the tube. Rotational movements of this knob rotatably adjust the tube 63 to position the proper combined altitude and air speed scale 62 in the slot 65 on the cover to permit reading of only one set of scales at a time.

The scales cooperate with an index S3 which is carried by the nut 3|, having a bearing connection therewith permitting it to. turni-about the nut 3| when: the frame 361s inclined. The position of the index 68 (and the nut 3|) may be manually controlled or set by the handwheel 51 which operates the gear E8 through a friction clutch 69 which prevents forcing or straining of the mechanism and of the timing links. The gear 68 drives the pinion IG and operates the screw 32 through the differential 6I. This preliminary setting of the nut 3l is accomplished before the synchronizing operation in order that time may be saved, making it unnecessary to follow the target for an exceedingly long period of time.

The position of the guide bracket 56 for the proper speed of operation of the sighting link 25 is determined by the rotational movement of the shaft 55. This shaft is fixed to a gear 'Il at one end thereof which meshes with a gear 'l2 carried on a threaded shaft 73 which is suitably mounted for rotational movement in the housing 23. On the other end of this shaft 13 is a bevel gear 'M which is driven by a bevel gear 'I5 carried on a shaft 76. The upper end of the shaft i6 is driven by a bevel gear 1l which ls driven in turn by bevel gear 18 fixed to the end of a threaded regulating shaft 19. Between the bevel gear 'il and the upper end of the shaft 16 is a suitable gimbal connection 80 so thatthe proper driving connection is maintained between gear 1l which is journaled on the standard 2| and shaft 'i6 which moves with the suspended housing 23. The regulating shaft 19 is rotated by a manually controlled handle 8|, which permits rapid and approximate regulation of the position of the friction Wheel 55 by operation of the handle device 8| as a lever, and permits slow and accurate regulation by rotating the control knob 82 about its shaft 83. 'I'his motion of the handle device 8|, as a lever, is indicated by a handle index |3| provided on the top of the handle device and cooperating with a scale |32 provided on the standard 2|. This index and scale permits the approximate setting of the handle device (which approximately sets the friction wheel 55 in accordance with the altitude and average speed) thus reducing the time required for the synchronizing operation, the scale |32 being graduated in accordance with the altitude. After roughly setting the handle device in accordance with the altitude indications of scale |32, asecond approximate or rigid regulation of the position of the friction wheel 55 is obtained by' pulling or pushing the handle 8i bearing 84. Fixed to the handle 8| is' a gear 'segment 85, which drives a train oi' reduction gears 8E, 8l, and 88, `the latter being xed on shaft 19. A differential 89 provided between the knob B2 and the handle Si prevents the rotathe shaft es, is rotated throughk the diaerennai 83. On thelupper end of the shaft 83 is fixed pivotal gear 90 which meshes with a pivotal gear 9| fixed on shaft 19. When the knob 82 is turned the handle 8| is swungforwardly or backwardly,

in accordance with the direction of turning, thus giving an indication automatically of the direction of rotation of the knob 82. showing the operator whether the knob `82 is being properly turned as he can feel the way in which the lever 8| is swinging, thus preventing confusion.' The rotational movements of the knob 82 are so arranged as to provide for a rather slow turning of the shaft 19, but when the lever 8| is swung on the bearing 84, a rather large angular movement of the shaft 19 obtains.

0n the shaft 59 is fixed the sun gear of the differential S2, the planetary gears of the differential being carried by arms which are rotatably sup` ported on the shaft 5S. The shaft 59 may be rotated through the gears TI and 12 when the shaft 'i9 is rotated, but every time the shaft 19 is moved, the screw 32 will be driven through the gears |35, |34, |33, and the differential S2, to move the nut 3| backward or forward when the handle 8| is operated. The screw 32 at this time is being moved by the friction disc device so that the line of sight will follow the objective. but the speed of movement of the sighting member may be too slow, in which case the objective moves oil' of the line of sight. If the speed of the sight member is corrected this would still leave the objective displaced from 'the line of sight, so each time the speed of the sight member is changed, the objective isv automatically brought back to the line of sight by superimposing on the normal movements of the screw 32, an additional movement through the differential 92 as previously explained. In this way the sighting member is automatically stepped up forwardly or backwardly, the lower end of the sight ing member moving backward with respect to the direction of travel of the aircraft as the speed is increased and moving oppositely as the speed is decreased, returning the objective to the line of sight in an automatic manner.

The angular. movements of the handle 8| are limited by a stop |12 shown in the form of a stud fixed thereon and projecting in to a segmental slot |13 which is concentric to the shaft 19 and is provided on the end of the support 2|.

It will now be apparent, assuming the motor 46 to be in operation and driving the micrometric screw 32 through the variable speed transmission, the manipulation of handle 8| may cause rotational movements of the threaded shaft 59 and position the bracket guide 55 in such a location as to cause the nut 3| to move along screw 32 at such a speed that the optical line of the sighting member appears to follow the movement of the objective,

To impose a substantially. constant torque or driving erort on vthe motor as the driven I'ricl tion wheel 55 moves at high or lov:r speeds, i

Iricln'on drag is imposed on the disc 54 in such l a way that the total torque required to dnve the y wheel 55 and the friction drag is substantially ccnstantrcgardless of the position of the 'friction wheel 55. y This drag is shown in the form of a suitable drag member S3 in rubbing engagement with the rotating disk 56 and carried a xcd distance away from thewheel 55 by the arms 8| extending out from the lower end of the bracket guide 55. When the friction drag 83, which preferably does not transmit the friction torque to the shaft 59,1is substantially at the Acenter of the disc `54, and its retarding elect is substantially zero, the friction wheel 55 is at its Amaximum distance from the center. When, however, the driving friction wheel 55 is moved towards the center of the disc 54 and the torque required from the motor is reduced. the drag member 93 is effective at a substantial distance von the other side of the center of disc 54 so that the combined torque effect of the two parts engaging disc 54 is substantially constant.

'Ilie-exact--time`at which the bomb is to be dropped so that it majalgipol the objective shownminnthe form. of a pivoted slottedV lever.

A This tiillngumgmbeLengages-a pin 96 carried onwast'op slide 91 whichslides ely'along the icrometric screw 32. This slide carries a stop ontact S8 which cooperates with a movable .contact 98 carried by the nut 3|, at the time of omb release, these contacts being connected e ectrically to the battery 49 and to a bomb rel ase device 209 to be later described.

Another electric contact |00 carried by the nut 3| is used for energizing a warning sign. This contact |00 is longer than contact 99, and cornes into Contact with S8 e. little before the releasing time of the bomband lights lamp |0|, as a warning sign, while contacts S3 and 99 light the releasing signal lamp |02 at the instant of bomb release. The lamps |0| and |02 are placed in the sighting field of the sighting member 26 as shown in Figs. 13 and 14. A third lamp |03 is for lighting the reticle of the sighting member for night bombing operation.

Lamps |0| and |02, through prisms |04 and |05, project written signs in the iield of the telescope, such for example as W" and R, see Fig. 13, meaning warning and releasing moment of the bomb respectively. The three lamps are enclosedin separate compartments.'

The timing member S5 is connected at its upper end to a pin |06 provided on an altitude slide |01 which is vertically mounted for sliding movement in a guide frame |08 xed on a side of the supporting housing 23. The slide |01 is raised and lowered to its proper position in accordance with the altitude of bombing, or vertical elevation, by a screw |08 which threads into the slide |01, the screw |09 being rotatably mounted in the guide frame |08 and carrying a gear H0 at its upper end. This gear H0 meshes with an intermediary gear engaging gear H2 carrying a drum ||3 on which are engraved altitude scales H4. On gear l l2 is xed a bevel gear l5, meshing with bevelgear lili, controlled by the manually operated `altitude control knob H1. The shaft H8 on which is xed the drum I3 turns in bearing ||9 fixed to the housing 23. On the same shaft H8 is fixed a cam |20,`see Figs. 4 and 18. the purpose of which is to correct automatically the tangent or' the trail and wind dection according to the altitude, as will be de- The drum H3 is controlled manually as previously mentioned, by the knob H1, this control being in accordance with the particular type` of bomb and in accordance with the altitude of the airplane. The altitude scales IH on the drum 5 ||3 are preferably arranged in separate sets indicating and computed in accordance with the actual falling time of the bomb, that is the vacuum time as modiiied by the time lag dependent upon the type or bomb, and also taking into e vnsideration the personal lag which is a function of the time and of the ground speed. Thus the sets Hla, Hb, lilo, and Hdd ol.' altitude scaes as shown in Fig; 16, indicate the actual falling time of the bomb without personal lag corrections, while the sets Hm', lllb', Hic', and Hdd' indicate the vacuum time as modilied by the time lag and personal lag. The sets H411'. IHb'. ||4c', and ||4d are for use when the device is to be manually operated. These scales are cooperatively associated with a cylindrical shield |2|, see Fig. 17, which has a series of openings |22 and which encloses the various sets of scales leaving only parts of the scales visible through the openings. This shield |2| may be turned manually about its vertical axis to arrange the proper opening with respect to the proper scale.

YThe openings'are arranged in pairs, two openings being thus provided for each type of bomb. One opening is for cooperation with the scale 00 Illa for automatic release while the other opening of a pair cooperates with the scale Ha', :for manual release,.openings being provided for the other scales as will be obvious. At each opening there is an index |23 for cooperation with the altitude scale. Thus for instance i1' a type A bomb is to be released automatically the shield 12| is turned until the second opening from the left of Fig. 17 coincides with the slot |24 of the sleeve |25 which is xed on the housing 23. The exact position of the opening |22 is preferably determined by means of a notch |25 provided in the sleeve |25 and cooperating with a spring pressed stop |21 having a spring arranged in.l the knob |28 ofthe sleeve as shown in Fig. 20. 'I'he engagement of the stop in the notch is such that holding tendency of the stop may be overcome when the lmob |28 is turned.

The timing member is iulcrumed on a pin |29 which projects laterally from the bracket guide 58, this pin slidingly supporting the member 95 by means of the slot |30 in the latter. The timing member 95 is thus set in its proper position when the bracket guide 5B has been moved to a position so that the sighting member follows the objective. This accurately determines the position of the stop slide 91 and stop contact 98 as to effect the release of the bomb at the proper instant. It will be understood that the timing member 95 is thus set or positioned in accordance with' the altitude, and also adjusted horizontally in an automatic manner in accordance with the speed of the movable sighting member. 4 lThe slide stop contact 98 carries an index |33 cooperating with a scale 98a graduated in degrees, see Fig. 3. The purpose of this device is to indicate the range angle of the preceding bombing operation and also to indicate the position of index E6 in relation to index |36 while the 70 micrometric nut 3| is approaching the slide stop 98.

Reference to Figs. 18 and 19 of the drawings, which show diagrams of an apparatus constructed .in accordance with the present invention, in-

dicates that the `bomb may be released at the proper instant so that it will hit the objective. In this diagram trail corrections and wind deiiections are considered. l

XX, YY, ZZ are the axes of a three-coordinate system. (See Fig. 21) Xi X: is the axis of the micrometric screw 32 Y1 Y1 is the axis of the guide 59 Z1 Z1 is the ground P is the pin 30 oi nut 3l R is the position of pin 96 of adjustable slide 91 at moment oi' bomb release O is the pivoting pin 55 of the sighting link 25 (trail considered) is the pivoting pin of the sighting link 25 (trail not considered) OP is the sighting line at the beginning of the synchronizing operation OR is the sighting line at moment of bomb release I1 R1 is the range, see Fig. 23

Va is the air speed W is the wind' speed' Vg is the ground speed Vr is the relative speed Vs is the speed of a moving objective O Ri' is the range for a fixed or moving objective, indicated in Fig. 22

0 Bo relative range for movable objective Ri' Ae :A11 corrected trail Rf R=temperature correction of trail Ri =trai1 correction according to elevation of objective Rf R=trail correction according to actual altitude of bombing l R1 Ao'=Bi I1=Ao' R1' cos N O AML-ground component of corrected trail for fixed objectve Mo' De'="/o Do=O GozAo' R1' CGS N O Us: relative component of corrected trail for moving objective ponent for xed objective Bo' Do'=Bo Du=0 Eo=Ao' R1' sin N O Un: deflection component for moving objective Angle N O A'=angle Ri Ao' R1' is the drift angle' Angle Au' O Uu=angle of approach for moving position of airplane when synchronizing operation is started Oo point of bomb release Ba position of moving objective at instant of bomb release Be R1' is the path of moving objective during falling time oibomb h is the basic height of the instrument X is a variable which is a function of T which in turn is a function of H and of type of bomb T is the actual falling time of the bomb t is the falling time in vacuum Y At is the time lag depending upon heights and type ci bomb tp iskthe personal lag K is a coeilcient of speed R is the radius oi the variable speed disc k is a coemclent depending upon air density in relation with height of plateau to be v bombed kt is a correcting coefficient depending upon atmospheric temperature affecting terminal velocity of bomb kn is a. `correcting coeilicient for trail angle according to actual altitude of bombing It can be proved that ii we make and the tangent of the relative range angle when bombing a moving objective is equal to (cos 180AN)} sin A)'OU0}i which are the formulae upon which the instru- -ment operates.

The function :nism heretofore described.

The value Rg Ao which is the trail for the particular type of bomb and air speed, average altitude, a deinite atmospheric temperature, and with objective at sea level as shown in the upper 4diagrammiatie illustration of Fig. 18, is determined by setting the terminal velocity scale l31 and air speed index s xed to the housing 23.

' and DEL-KV, or KVf and if the airplane is dying adrift, the tangent ot the range angle is equal IIfhis value Rf An'. however, is not correct but is corrected so as to bring the point P.; been' to R? and simultaneously virornlt to R12 in order to correct foiv the atmospheric temperature and for the height of the objective above sea level, this being done by setting the air density dial |56 on the temperature index |51; and then the point Rf is moved back to R1' to correct for the actual altitude of the airplane and the particular type of the bomb. this correction belngmade by cam controlled by altitude scale ill operated by handwheel The terminal velocity is set on a drum |39 (Fig. 18) having a threaded part |40 for operating with a screw |4i. which extends into the housing and carries a pivot |42 about which the link |43 is rotatable. The liniey |43 hasnrigid with it an arm |44 on which is provided a stud or arm |45. Screw |4| is prevented Iromturning about its axis by an arm |46 which bears against two guide bars |41. The stud |62 of slide |6| is shown in position .1I in Fig. 18. The correction obtained at sea level by means of arm |44 and part |4| is Iba multiplied by various leverageson the sight. or R2 An' on the ground and gives p the tangent of the trail angle for average altitude for the particular type of bomb and for the parvtlcnlar air speed.

The correction Rf R is obtainedby setting the air density dial |56 on temperature index |61 in accordance with the actual atmospheric temperature,

The correction R R? is obtained by setting the air density dial |56 on temperature index |61 in accordance with the height of the objective, the dial |56 cooperating with index |51 iixed on housing 23 and moving the link |63 through the gears |58, |59, screw and sliding member |61 carrying stud |62 about which the link |43 rotates. At sea level and for particular temperatures stud |45 carried by the arm |44 is at position bo. In turning the dial |56 up to a determined temperature index value at |61, the stud |62 will be set at position II andsince stud |42 is iixed. lever |43 will rohtoabout the stud |42, wlrl'yins the right-hand end of stud |45 to position bi for objective above sea level and for actual temperature.

ARi=K(Ri-A) The correction thus obtained is bo b1 multiplied by various leverages on the bomb sight corresponding to Rf Rf on the ground. The stud |65 o! drift correcting device is at position I corresponding to drift angle equal zero, and

lever |63 pivoting about |55 transmits the movement of |45 to |64 which pushes lever |65 and slide 40 respectively, since link |69 rigid with |66 pivots about |68. The slide 4i! is displaced longitudinally a distance equal to tion in accordance with any particular altitude of bombing. This is obtained by means of the altitude cam |20, iixed on the shaft H8, which carries altitude scaleL i4. The cam |20 cooperates with the stud |66 which is attached to the sliding member |67 carrying a stud |68 pivotally interconnecting the linl; |69 to the slide. The arm |65 is rigid with link |69, which pivots about axis |70 carried by the arm l'll which is iixed to the longitudinal vslide 40. At average altitude, the stud |68 is at position I, and at position II for some particular higher altitude. The displacement of stud |68 from I to II causes the correction RiRi m' (RiA)=K(RiA) and the total corrected trail will be Ri' Ao' on the mund;

(see Fig. 18).

When bombing an objective situated at sea level, from average altitude and at a. fixed temperature the trail correction is Rf An'. When bombing an objective situated at sea level from some average altitude and under some actual temperature the trail correction is Ri An'.

When bombing an objective situated above sea level from an average altitude and at some actual temperature the trail correction is RA. When bombing from some lower altitude with the objective above sea level and under some actual temperature the trail correction will be RrAo'.

The total corrected trail made by the slides |61 and |6|, and by the rod |4| is, therefore, Ri'An. This corrected trail line, however, is not on the ground course line, and to correct the trail for the ground course component or relative component if flying along an angle of approach with respect to the path of a movingobjectlve.' slide means are provided to accomplish this automatically in accordance with the angular movements of the sighting device, or in other words in accordance with the drift angle, or drift angle plus angle of approach if bombing a moving objective.

The entire standard2| may be swung about axis of the post 22 by means of a suitable handle |15 so that the sighting line of the telescope may point directly at the objective, in case there is a cross wind prevailing or cross wind combined with angle of approach Ao'OUo. This swinging of the standard 2|, and consequently of the supporting housing 23, operates the pilot director shown in Figs. 5 and.9, and also causes the rotation of the bevel gear |49 (Fig. 18); the bevel gear |48 being Xed on stud i'l which has a key |16 setting in slot |'|'l of post 22 which is xed to the Y fuselage of the airplane, thus preventing gear |46 from turning about its axis when the standard 2| is swung. Therefore, the swinging of the standard 2| causes the rotation of bevel gear |49, the sliding gimbal joint |50 and the cam ISI cooperating with lever |52, see Figs. 18 and 6, which pivots about axis |53 iixed to the housing 23. The fork of lever |52 cooperates with a sliding member |54 on which is fixed a stud |55, about which pivots lever |63. The rotation of cam iSi causes the displacement of stud |55 from position I corresponding to drift gear |83 being fixed on the shaft |84 which carries cam |5|, so that when swinging the standard 2| about its vertical post 22, cam |18, rotatesthrough an angle S equal to the drift angle NOAn', or through an angle S' equal to the drift angle plus angle of approach, so as to keep the geometric plane Oe-Ne of the cam |18 always parallel to the axis ON of the fuselage of the aircraft whatever the drift angle or angle of approach may be.

The cam |18 cooperates with a stud |85 fixed to the transverse slide 38 carrying the pivot 31 and pin 35 of the sighting member 25.

Since BI=a is the ground component of the trail reduced to the height hof the instrument, or GnO: the relative component of the trail reduced to the height h of the instrument, and since BI is making an angle S with respect to the fuselage or G00; making an angle S' with respect to the fuselage, and since the working surface OeNe of the cam |18 is always maintained parallel to the fuselage of the aircraft making an angle S or S' with the longitudinal axis of the sight, the slide 38 will move laterally a distance corresponding to for the relative deflection.

Since the bearings 42 and 33 of the frame 3S provide for rotational movements about axis 32, the lateral displacement fr' or e003 of the hinge 3'! carrying the upper part ci the frame 35 will cause the lateral inclination of the optical sighting line along a plane Ai'ORi making a deect-v ing angle RORo' with the vertical R'Oi or will cause the relative lateral inclination of the optical sighting line along a plane EoOoBo making a relative deflecting angle EaOoO with the vertical O50 thus making automaticy the deflection correction according to any particular type of bomb, any particular height, time lag, drift angle, angle of approach, speed and direction of moving objective, air speed, ground speed, elevation of the objective above sea level, and atmospheric temperature affecting terminalv velocity.

It will thus be understood that by means of the cam |73, a certain lateral movement of the upper end of the sighting member is obtained,

'and by means of the cam l5! and its slide |54. a

certain longitudinal movement of the upper end of the sighting member is obtained, and together make correction RiAo' sin NOAo' or Ri'An' sin NOUo and Ri'Ao' cos NOAo or RiAo' cos NOUo when the bomb is released, therefore, it will strike the objective R1 instead of the thecgraduated in reet set on a drum |33 (Fig. 23) tiredv to the screw |85 which cooperates with the nut xed to 3l.

The setting oi the drum |88 (see Fig. 23) with respect to kscale |81 which is xed to the optical device 2S is made by 'turning knob |85.' The rotational adjustment of the drum and screw |85 moves the optical device a distance b5 and increasing the range by a corresponding amount, since this rotation of the screw moves the optical device bodily with respect to the frame 3E.

Another imethod of dropping bomb short" when automatic release is used, canv be obtained by estimating ashort distance on the ground` when sighting through the telescope and then" when said short distance is properly estimated, pull swiftly the main control 8| which through the train of gears 85, 88, 8l, 88, 18, 11,15, ld, l2, 1|, the differential 92 and gears |33, |34 and |35, will create an extra rotation of screw 32 and rapidly bring contacts 99 and 98 together which energizes magnet 209 and releases .the

bomb. Y

During that short instant in dropping '"short" the rapid pulling of control 8| also increases ,the speed of the nut 3| and simultaneously pushes the timing lever |29 forward, and the contact 93 respectively thus dropping bomb shortl without delay and at the will of the bomber. The stud |89 xed on drum |31 and 'stop |90 ixed on the housing 23 prevents the ber 25 is being changed, and to maintain the center of gravity of the suspended housing 23 constant, a compensating weight |9| (Fig. 4) is provided, this compensating weight being mounted on a screw |92 and connected by a suitable means to the nut 3i so that as the nut moves toward the center of the housing 23 the weight |9| will also move the proper distance to compensate for shifting of the effective weights of these various parts, and maintain the center of gravity oi the apparatus constant. As shown gear iixed on the micrometric screw 32 rotates screw |92 through gear-|93. At the base of the housing 23 is a slot |94 in which slides stud |95 which is fixed to the nut carrying weight |9|, thus preventing the weight from turning about its axis.

Movement oi the timing member 95, guide bracket 55, and slide 91 is also vcompensated for by means of a weight |96 which is in threaded engagement with the screw i3 so that as the timing member 95 and its associated parts move toward the left in Fig. 4, the weight |93 will be moved toward the right a proportionate amount to prevent the unbalancing of the suspended housing 23. To prevent the weight |96 from turning with the screw i3 the former is guided by a stud |97 which moves freely along guide |98 and which prevents rotational movements about the axis of the screw '|3.

The supporting housing 23, although mounted for free swinging movements both laterally and .longitudinally of the aircraft, is stabilized so that rapid or sudden changes in position oi the aircraft may be substantially ineiiective on the housing 23. The upper part of the housing 23 projects upwardly at |99 and carries a post 20B which is universally connected at 26| to the piston rod 23 of a iston operating in a cylinder 285 to provide a dash pot damping means for damping the movement of the supporting housing 23. A similar dash pot 206 is provided on 10 'lhe bomb 281 (Fig. 4) is mounted on a suitable-rack 208 and is releasable from this rack when a solenoid or electromagnet 209 is energized- One side of this electromagnet 208 is connected to one side of the battery 45 the other I5 side of the solenoid being connected to the contact $9 on the movable nut 3|. The other side ofthe battery is connected to a disconnecting4 'switch 2li! which however is closed when the i apparatus is to be used. The switch 2|!! is in so turn connected to the motor 45 through the regulating contacts 48, and also connected to electromagnets 2H and 2|8 and releasing signal light |02, as shown. Theelectromagnet 2|| is connectedto the stop contact 98.

When the electromagnet 2H is energized the armature of a starting lever 2|2 is attracted.

The lever 2|2 is provided with a hook 2|3 and cooperates with a stop 214 slidably mounted on the shaft 1S. I to this stop 2|4 toward the left by endwise movements of a spindle 2|5 which is provided with a knob 2|6 at its outer end, in a position to be readily pressed inwardly by the hand of the operator when hegrasps hold of the lever 3|. l5 A spring 2i? normally pressesl the knob 2|6and the spindle 2|5 toward the right, tending to hold the stop 214 toward the right in Fig. 4, in which position' the contact 25D will be open-circuited vin inoperative position. However, when the knob 2|B is pressed inwardly to the position shown in Fig. 4 the stop 2|4 will ride over the inclined cam surface of the lever 2|3 and close the contact 258, the stop 2i4 being held in its effective position against the action of the spring 2|1, by means of the hook on the lever 2|3.

The mechanism of the pilot directing device is enclosed in a housing 2|3 fixed to the standard 2| which is rotatably mounted on the post 22. This mechanism comprises a Worm gear 2|9 50 fixed to a. sleeve 220 rotatably mounted on the post 22. A friction spring 22| xed'at one end to the post 22 prevents the standard 2| from turning freely on the supporting post 22, see Fig. 11. On the shaft 223 guiding the worm 222 is 55 xed a pinion 224 meshing with gear 225 and turning in bearings 226. The shaft 221 is fixed to the gear 225 and the clutch part 228. A toothed wheel 229 together with clutch part 23D turns freely about the shaft 221. Clutch parts 50 23| and 232 are xed to the control |15 which is rotatably and longitudinally slidable in the bearing 233 provided in the housing 2|S. A spring 234 is provided to normally engage the clutches 228 and 23! in a constant manner so that the 65 control 115 is in constant engagement with the gear 225 and the worm gear 2|9.

On shaft 235 which turns in the bearings in the housing 2|8 are xed levers 236 and 231 and an electric contact lever 236. The lever 256 is 70 in engagement with the teeth or' toothed wheel 228. One end of the spring 239 is fixed to the housing 213 while its other end is attached to the lever 231, thus normally urging the contact lever 238 to a. central position, in a yielding manner, fl each time the lever 236 passes over a tooth of Sliding movements are impartedkstraight course.

thewheei 223. The contact lever 238 thus passes alternately from a central Contact 240 to a righthand contact 24| if the control |15 is turned to the right, and from the central contact 24B to Athe left contact 242 if the control turns in 5 the other direction. The central contact 240 is electrically connected to a central lamp 243, see

Fig. l0, preferably colored white, and meaning the aircraft toward the left side, when this lamp is illuminated. The contact 24! is connected to the right-hand lamp 245 indicating to the pilot 15 that he should turn toward the right when this lamp is illuminated. 'I'hese three lamps, all three different colorsare enclosed in a housing 246 which is located on the pilot's instrument board.

An electric cable 241 connects thebomb sight electrically to the battery, the bomb releasing device and the pilot director indicator.

In operation, the pilot director automatically tells thepilot in which direction he should turn or whether he should fly straight ahead, these 25 indicationsbeing given to him automatically as the bomber follows the objective and turns the bomb sight about its vertical axis, or'keeps it stationary with respect to turning movements.

Assume the aircraft is flying 'ofi its course, for 30 example toward the left. The central contact lever 238 has been at its neutralposition and the lamp 243 has been lit, the pilot having ilown a The bomber now, as the aircraft is flying ci course, toward the left, places 3 the sighting line on the target by swinging the standard 2| about the post 22 by pushing control knob |15 toward the target (right-hand side) without turning |15 about its axis. The lamp 243 is still lit and the aircraft is still flying in 40 a straight line oi course as just stated. The. bomber then follows the apparent and drifting motion of the target by pushing and turning the control |15 about its axis; in doing which the clutch parts 23S- 232 are engaged (clutch 45 parts 23|-228 remaining engaged) so that the toothed wheel 228 is rotated, the teeth of this wheel displacing the lever 236 toward the righthand side, thus moving the contact lever 238 over to contact 24| and lighting and causing the 50 energization of the lamp 245, the lamp 243 being deenergized. This indicatesto the pilot that he should turn toward the right, the indication being automatic. The bomber then releases the control |15 which disengages the clutch 232-238 55 and the central lamp 243 is'again illuminated and lamp 245 deenergized.

The course of the aircraft is thus partially `corrected, the bomber again adjusting the sighting line on the target by turning the control 6o about its axis. without giving any signal of turning. Then when the target appears to be drifting, the bomber pushes and turns the control H5 to give the necessary signal that the aircraft should be turned. The faster the target drifts from the sighting line of the telescope, the more rapidly the alternate energization of the lamps 243 and 245 or 243 and 244 will take place. The speed at which the alternations o the right-hand lamp or the left-hand lamp with the central lamp takes place indicates the amount of turn required. A very rapid correction of the aircraft with respect to the target can thus be obtained.

The -operation of the device is as follows:

The switch 2f!! being closed, the trail correction and other corrections are made by suitably setting drum |31, scale |51 and scale |88 if it is desired to drop bomb'ahead. Then the pickup angle is set by means of the scale 82 and index 65 by turning control 6l which through friction clutch 68, gears 88, 'l2 and diilerential 8| displaces the nut 3| forward or backward. The nut 3| is carrying'the telescope 25; 'Ihe standard 2| is then swung vabout the axis of the post 22 to make course correction as above described until the objective moves directly towards the observer when sighting along the telescope or the sighting member 2li.V The bomber then synchronizes themovement of the sight with the objective. He iirst grasps the handle 8| with his hand and in doing so he naturally presses inwardly on the knob 2||v to cause the spindle 2|5 to move inwardly and move the sliding stop 2H so that the spring 218 may push the hooked lever 2H upward to maintain stop 2M in hooked or effective position.

When being engaged by hook 2|3, the conical part of the sliding stop2l4 pushesup the spring contact 2&8 making contact with an insulated contact 25D connected to solenoids 2|| and 2|8 which are in parallel, and simultaneously energizes the motor 46 through regulator 41. The

.bomber then sights in the telescope 26 to see whether or not the optical lineis moving in synchronism with the objective. If not, the bomber pulls or pushes handle 8| which, through the gears 85, 85, 8T, 58, 18, 11, 15, 74, '12, and 1L.,

varies rapidly the-speed of rotation o! the micrometric screw 32, by varying the variable speed connection between the. motor and the screw 32.

Simultaneously, in varying the speed of screw 32 by operation oi' handle 8 through differential 82 and gears |33, |34, and |35, the nut 3| carrled byscrew 32 will be stepped forward or backward, thus catching the target rapidly and automatically with respect to the recticle of telescopeV 26.

For ilne synchronizing regulation, the bomber turns-lmob 82 which, through dierential 89, gears S8, 9|, 18, 1T, 16, 1t, 12, and 1|, varies slowly the speed of rotation of the micrometric screw 32 and as stated before. the nut moves forward or backward, thus catching automatically the target in respect to the recticle of the telescope.

This regulation of knob 82 is continued until the optical line of the telescope 26 remains synchronlzed with the objective, and in synchronizing the sights with the objective it Will be understood that the bomber has accomplished automatically the adjustment of the timing member so that the latter is properly set for the release of the `bomb at the proper instant. The bomber merely keeps regulating the knob 82 to maintain synchronization of the sights and the objective until the contacts 98 and S9 engage.

An instant before contacts 98 and 98 engage, contact 98 engages with warning contact |28 which lights the warning lamp lili in the telescope 25.

When contacts 9S and 8.8 engage, it is the bomb releasing time, and vreleasing signal lamp |62 indicates to the pilot that the bomb should be released if releasing is to be made by hand, or indicates to the bomber that the bomb has been released if said operation is made automatically.

When this occurs a circuit is completed through the battery 8, the solenoid or electromagnet 289,

and through the electromgnet 2| l. the result ingthe instantaneous dropping oi' the bomb.

Another result is the attraction and lowering of the hook 2|3, due to energization of the electromagnet 2H which thus releases sliding hook stop 2H which cuts the circuit between contacts 248 and 250, thus interrupting the circuit through signal lamps |8| and |02 and through motor 48 which stops.

Another result of the engagement of contacts 88 and 99 is the energizationof the solenoid 2|8 which automatically places the handle 8| at its original position, and simultaneously places the timing lever 85 in a normal vertical positiomthus separating contacts 98 from 59, preventing the accidental release of another bomb if the bomber accidentally pushes knob 2|6, and preventing jamming of the apparatus by accidental subsequent operation of control 8|. solenoid 2|8 is connected to the handle 8| by means of a steel ribbon 22, one end of which is fixed to the plunger, the other end to a stud 253 xed to the segment gear 85 so that the return of the handle 8| to its normal position may be accompllshed.

To reset the synchronizing nut 3| so that it is in position for a second bombing operation, the screw 32 is rotated manually by handwheel 61 to place the optical line of the telescope at the proper pick-up angle. Then, the general operations of the sights are started again as .JuSt describe-(L V The operation of the device is quite simple, considering the extremely accurate results that may be obtained and the number of correction The plunger of factors that are taken into consideration. The y probability of human errors are to a large part obviated, and the apparatus may be operated very quickly and yet with extreme accuracy. While the device is provided with adjustments for the correction of many factors, it will be apparent that all of these correction adjustments need not be employed i! it is desired to neglect the errors arising.

'While the i'orm oi' apparatus herein described constitutes a preferred embodiment o! the inventiomit is to be understood that the invention is not limited to this precise form of apparatus, and that changes may be made therein without departing from the scope of the invention which is defined in the appended claims.

What ls claimed is:

1. In a sighting device oi the class described, a movable sighting member adapted to be trained on an objective to follow the relative movement between an objective and the sighting device, means for laterally angularly adjusting said member to` compensate for wind deflection and Ving lever to determine the moment of bomb release. l

2. In a sighting device of the class described, a

movable sighting member adapted to follow the relative movement between an objective and the siglrting device, an adjustable timing member,

means for adjusting said timing member so that it is set in accordance with the proper time of bomb release, supporting means ior saidmemmeans, a standard, a universal connection between said standard and said supportingmeans,

' 5 damping means for damping the movements of said supporting means, and weight means car. ried by said supporting means and operably connected to one oi said members for automatically compensating weight unbalance due to movements of said member.

3. In a sighting device of the class described, a A movable sighting member adapted to follow the 1 relative movement between an `objective and the sighting device, an adjustable timing member. 15 means for adjusting said timing member so that the proper moment of bomb release is determined, power means for moving said sighting member, speed changing mechanism between said power means and said sighting member, manual- 20 ly controlled means for adjusting said speed changing mechanism to cause the sighting member to :follow the relative movement between an objective and the sighting device, means for energizlng said power means automatically upon starting operation of said manually controlled means, and means for automatically deenergizing said power means after a synchronizing operation has been completed.

4. In a sighting device of the class dcribed, a i

movable sighting member, an adjustable timing member, motor means for moving said sighting member, and a control device for controlling the speed of said sighting member having provision operable as a lever for rapidly changing the speed g and additional means provided as a part oi said. lever for slowly changing the speed.

5. In a bomb sighting device oi.' the class described, a movable sighting member, means for causing said sighting member to follow the relao tive movement between an objective and the sighting device, an adjustable timing member determining the moment ci bomb release, a stationary sign in the sighting ileld of vision, and means for illuminating said vsign substantially at the time of bomb release.

6. In a sighting device ot the class described, a sighting member movablein accordance with the relative movement between an .obkctive and the sighting device, an adjustable timing meni-v ber, an element operated by said timing member and cooperating with said'sighting member to determine the time for projectile release, and means for adjusting one of said members manually comprising a series of separate scales, and an adjustable index member cooperating therewith and having a series of openings that may be brought into view selectively, each scale oooperating with one of said openings and visible therethrough.

a movable sighting member adapted to follow the relative movement between an objective and the g5 `Sighting device, means adjustably supporting one 7. 1n a sighting device ot the class described,

therefrom, and a compensating mechanism interconnecting said manually positionable means and said sighting member for automatically stepping the sighting member forward or backward as the speed is changed to quickly move the d sighting member toward the line ci the target.

9. In a sighting device oi the class described. a movable sighting member including an optical part adapted to be trained on and follow the movements of an objective, an adjustable timing member, means for positioning said timing member in accordance with the angular speed of said sighting member in following a target, an element operated by said timing member and engaging with said sighting member at the time for projectile release, a support for said members, a pivotally mounted frame carrying said sighting member, and means for tilting said frame about a fore and aft axis to automatically tilt said optical part in accordance with wind deilection duetto the drift angle and angle of approach of the sighting device with respect to vthe objective.

10. A bomb sighting device for aircraft comprising an angularly movable sighting` member adapted to follow the relative movements between an objective and the sighting device, an adjustable timing member, means' for' positioning said timing member in accordance with the angular ,speed of said sighting member'in iollowing a target, an element operated by seid tim-` ing member and engaging with said sighting member at the time for projectile release, a xed support, a housing adjustable on said support. and carrying said members, a longitudinally ari--l ing member laterally as said housing is rotated on said support to tilt said sighting member about said axis, and means for longitudinally adjusting said carrying member to longitudinally adjust the sighting member without alteration to its angle of tilt.

l1. -A bomb sighting device for aircraft com-- prising an angularly movable sighting member adapted to follow the relative movements between an objective and the sighting device, an adjustable timing member, means for positioning said timing member in accordance with the angular speed of said sighting member in following a target, an element operated by said timing member and engaging with said sighting member at the time for projectile release. a stabilized support for said members, means rotatably mounting said support on a fixed vertical axis, slide means operable in accordance with rotational movement of said support on smdxed vertical ev" adlustably tilting said sighting memr laterally with respect to the direction of traveLand means connected to said slide means for correcting the trail deection in accordance with the sines of the drift angle and the angle of approach as the support is rotated on its vertical axis.

12. In a sighting device of the class described, a movable sighting member adapted to follow the relative movement` between an objective and the sighting device, an adjustable timing bar, means for manually adjusting the upper end of said timing bar in accordance with vertical elevation, means for adjustably setting an intermediate portion of said timing bar in accordance with the speed of the movable sighting member. a timing element cooperating with the sighting member and positioned by the lower end of said timing bar, and compensating means for said members for compensating for wind deec tion and trail correction.

13. In a sighting device of the class described. a movable sighting member having a Asight adapt- 'ed to be trained on the objective to follow the movement between an objective and the" sighting device, manually controlled power means for moving said sighting member so it follows the apparent movement of the objective, an adjustable timing member having a pivotal support, l

means for vertically adjusting said pivotal support to set said timing member in accordance with vertical elevation. means for moving a portion of said sighting member. in the direction of the ground speed course to compensate the line or sight for trail correction, and means for adjustably setting said timing member in accordance with. the speed oi said movable sighting member.

14. In e sighting device of in@ dass described, 1r

A movement between an objective and the sightlng device, an adjustable timing member cooperating' with said sighting member to determine the time of projectile release, a pivotal support an objective and the sighting for the upper end of said timing member. means for vertically adjusting said pivotal support to set said timing member in accordance with vertical elevation, a pivotal support for the other end of said sighting member, means for moving said .last named support and sighting member in a member and said manually controlled means to constantly correct the adjustment of said timing member up to the time o-f projectile release in accordance with the speed of the movable sighting member.

15. ln a sighting device of the class described, a movable sighting member having a sight at its lower end, power means for longitudinally moving one end of said sighting member, manually controlled'but normally stationary means for governing said power means so that said sighting member follows the relative movement between device, an adjustable timing member cooperating with said sighting member to determine the t'me of projectile release, a pivoted support for the upper end of said timing member, means for adjustably setting said pivotal support in a vertical direction in accordance with vertical elevation, a pivotal support for the other endof said sighting member,

means for pivotally moving said sighting member on its support to tilt said sighting member transversely of the ground course to compensate for lateral wind, means for moving said last named between an objective and the sighting device, a.

constant speed motor controlling the movements oi' said sighting member, a driving connection between said motor and said sighting member, said driving connection including a variable speed drive. a manually controlled member, and mechanical connection -from said member to said A variable speed drive to vary the speed of movement of said sighting member and cause it to follow the movement of the objective, an adjustable timing member, means connecting said member to said mechanical connection so that said timing member is automatically positioned in accordancc with the speed of movement of said sighting member, means for adjusting one portion oi said timing member vertically `in accordance with vertical elevation, means for adjusting one portion of said sighting member longitudinally parallel to the ground course for trail correction in accordance with wind deflection, and additional means for adjusting said sighting member in a direction transversely of the ground course in accordance with the wind deiiection.

17. In a sighting device of the class described, a movable sighting member, a constant speed motor for operating said sighting member, a manually controlled variable speed drive between said sighting member and said constant speed motor, an adjustable timing member, means for adjusting a part of said timing member vertically in accordance with altitude, means for adjusting a part of said timing member horizontally in accordance with the speed of the sighting member, means for adjusting one portion of said sighting member transversely of the ground course in accordance with wind deection and additional means for adjusting said sighting member to change the line of sight in the vertical plane of the ground course in accordance with air resistance on the bomb.

18. In an aircraft, a bomb sighting device of the class described, comprising a. movable sighting member, means for causing said sighting member to follow the relative movement between an objective and the sighting device, an adjustable timing member determining the moment of bomb release, a support for said members, turning means rotatable on the support for turning said support about istl a vertical axis, an automatic signal means profor each lamp, a control finger selectively engage- 75 able with the energizing contacts, means normally maintaining said finger in engagement with the contact for one of said lamps, and means on said turning means for controlling the position of said control ilnger. I

19. In a bomb sighting device of the class described, a movable sighting member adapted to follow the apparent movements of an objective, an adjustable timing member, a. support for said sighting and timing members mounted for turning movement on a vertical an element operated by `said timing member and cooperating with said sighting member to determine the time for projectile release, means for adjusting said members in accordance with altitude and bomb A scribed, a movable sighting member adapted to follow the relative movement between an objective and the sighting device, an adjustable timing member, an element operated yby said timing member and cooperating with said sighting member to determine the time for projectile release,

means for adjusting said sighting member in' accordance with altitude andi bomb time lag,

'means for adjusting said timing member in accordance with the speed of said sighting member,lateral adjustment means for tilting the sighting member laterally of the actual path of travel in accordance with the drift angle and angle of approach, and differential slide means for adjusting the sighting member in the direction of actual path of travel for correcting the trail in accordance with the altitude,'tempera ture and drift angle.

21. In a bomb sighting device of the class described,`a movable sighting member adapted to follow the relative movement between an objective and the sighting device, an adjustable timing member, an element operated by said timing member and cooperating with said sighting member to determine the time for projectile release, a support for said members, means for adjusting said sighting member in accordance with 1 altitude and bomb time lag, means for adjusting l said timing member in accordance with the anguiar speed oi' said sighting member, mechanism for angularly adjusting said sighting member in said support laterally of the ground course direction in accordance with the sine of .the drift angle and angle of approach, and mechanism for adjusting said sighting member longitudinally in said support in accordance with drift angle,

air speed, type of bomb and altitude of sighting device.

22. In a sighting device of the class described,`

a movable sighting member adapted lto follow the relative movement between an objective and the sighting device, power means controlling said sighting member and including a speed .changing device for controlling the spe'ed of said sighting member, an adjustable timing member, an eiement operated by said timing member and cooperating with said sighting member to determine the time for projectile release, means for angularly adjusting said timing member from a inormal vertical position in accordance with vertical elevation, meansv operable from a. normal position for adjustably setting said timing member angularly in accordance with the speed of the movable sighting member, and means for automatically returning said speed changing device and said adjustable timing member to normal 'positions when' said power means is deenergized.

23. In a. sighting device of the class described, a movable sighting member adapted to follow the apparent movements of an objective, an adjustf able timing member, means for controlling the speed of movement of said sighting member. means for adjusting said timing member in accordance with thespeed of said movable sighting member, means for `adjusting one of said membersin accordance with vertical elevation, a housing enclosing said timing member, said movable .sighting member including a sighting tube-arranged externally oisaid housing and supported for pivotal movement relative to said housing about axes substantially parallel to and substantially transverse of the line of flight.

24. In a sighting device of the class described, a movable sighting member adapted to follow the apparent movements oi an objective, an adjustable timing member, means for adjusting said timingv member to determine the proper time for bomb release, a housing enclosing said timing member, said movable sighting member including an externally arranged sighting tube supported on said 'housing for movement about an axis transverse of the line of flight and for movement about a second axis substantially paralle] to the line of ight.

V(ancianas .1.. Es'roPPnY.

as l' 

